EP2903764A1 - Method for repairing a component for use in a turbine engine - Google Patents

Method for repairing a component for use in a turbine engine

Info

Publication number
EP2903764A1
EP2903764A1 EP13779463.2A EP13779463A EP2903764A1 EP 2903764 A1 EP2903764 A1 EP 2903764A1 EP 13779463 A EP13779463 A EP 13779463A EP 2903764 A1 EP2903764 A1 EP 2903764A1
Authority
EP
European Patent Office
Prior art keywords
component
powder
mating surface
coupon
powder coupon
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP13779463.2A
Other languages
German (de)
French (fr)
Inventor
Allister W. James
Zafir A. M. Abdo
Ahmed Kamel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens Energy Inc
Original Assignee
Siemens Energy Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens Energy Inc filed Critical Siemens Energy Inc
Publication of EP2903764A1 publication Critical patent/EP2903764A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • B22F7/08—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools with one or more parts not made from powder
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
    • B23K35/02—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by mechanical features, e.g. shape
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
    • B23K35/02—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by mechanical features, e.g. shape
    • B23K35/0222—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by mechanical features, e.g. shape for use in soldering, brazing
    • B23K35/0244—Powders, particles or spheres; Preforms made therefrom
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00—Restoring or reconditioning objects
    • B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
    • B23P6/005—Repairing turbine components, e.g. moving or stationary blades, rotors using only replacement pieces of a particular form
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/005—Repairing methods or devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P11/00—Connecting or disconnecting metal parts or objects by metal-working techniques not otherwise provided for 
    • B23P11/02—Connecting or disconnecting metal parts or objects by metal-working techniques not otherwise provided for  by first expanding and then shrinking or vice versa, e.g. by using pressure fluids; by making force fits
    • B23P11/025—Connecting or disconnecting metal parts or objects by metal-working techniques not otherwise provided for  by first expanding and then shrinking or vice versa, e.g. by using pressure fluids; by making force fits by using heat or cold
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/22—Manufacture essentially without removing material by sintering
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade

Definitions

  • the present invention relates to repairing fully consolidated components for use in turbine engines using partially sintered or bonded powder coupons that are shrunken onto and bonded to the fully consolidated component with a bonding agent.
  • a turbomachine such as a gas turbine engine
  • air is pressurized in a compressor section then mixed with fuel and burned in a combustion section to generate hot combustion gases.
  • the hot combustion gases are expanded within a turbine section of the engine where energy is extracted to provide output power used to produce electricity.
  • the hot combustion gases travel through a series of stages when passing through the turbine section.
  • a stage may include a row of stationary airfoils, i.e., vanes, followed by a row of rotating airfoils, i.e., blades, where the blades extract energy from the hot combustion gases for providing output power.
  • a method for replacing a removed damaged portion of a fully consolidated component for use in a turbine engine.
  • a powder coupon is provided comprising powder particles that are at most partially sintered or are bonded together with a binder.
  • a bonding agent is applied to at least one of an outer mating surface of the component and an inner mating surface of the powder coupon.
  • the powder coupon is positioned over the component such that the inner mating surface of the powder coupon is located adjacent to the outer mating surface of the component with the bonding agent therebetween so as to form a replacement assembly comprising the component, the powder coupon, and the bonding agent.
  • Heat is applied to the replacement assembly, wherein the applied heat fully sinters the powder particles of the powder coupon so as to bind the powder particles together, thus causing the powder coupon to shrink onto the component.
  • the applied heat also activates the bonding agent to bond the inner mating surface of the shrunken powder coupon to the outer mating surface of the component.
  • the applied heat to the replacement assembly does not sinter the material forming the fully consolidated component.
  • a method for repairing a fully consolidated component for use in a turbine engine.
  • a damaged portion of the component is removed, and an outer surface of the component adjacent to the location of the removed damaged portion is machined using a material removal procedure to form an outer mating surface comprising a stepped surface with an adjacent portion of the outer surface of the component.
  • a powder coupon is provided comprising powder particles that are at most partially sintered or are bonded together with a binder.
  • a bonding agent is applied to at least one of the outer mating surface of the component and an inner mating surface of the powder coupon.
  • the powder coupon is positioned over the component such that the inner mating surface of the powder coupon is located adjacent to the outer mating surface of the component with the bonding agent therebetween so as to form a replacement assembly comprising the component, the powder coupon, and the bonding agent.
  • Heat is applied to the replacement assembly, wherein the applied heat fully sinters the powder particles of the powder coupon so as to bind the powder particles together, thus causing the powder coupon to shrink such that the inner mating surface of the powder coupon is shrunken onto the outer mating surface of the component with the bonding agent therebetween.
  • the applied heat also activates the bonding agent to bond the inner mating surface of the shrunken powder coupon to the outer mating surface of the component.
  • the shrinking of the powder coupon onto the component exerts a pressure on the outer mating surface of the component so as to aid in the bonding process between the inner mating surface of the shrunken powder coupon and the outer mating surface of the component.
  • the applied heat to the replacement assembly does not sinter the material forming the fully consolidated component.
  • Fig. 1 is a schematic illustration of a component for use in a turbine engine of the type to be serviced in accordance with the present invention, wherein the component includes a damaged portion;
  • Fig. 2 is a schematic illustration of the component illustrated in Fig. 1 after a step of a servicing operation has been implemented to remove the damaged portion from the component;
  • Figs. 3 and 4 are perspective (Fig. 3) and schematic (Fig. 4) illustrations of the component of Fig. 1 undergoing another step in the servicing operation;
  • Fig. 5 is a schematic illustration of the component of Fig. 1 after it has undergone the servicing operation according to the present invention.
  • a turbine engine component 10 of the type to be serviced according to an aspect of the present invention is illustrated.
  • the component 10 is a turbine blade 10 having a damaged portion 12 to be replaced, although it is noted that the invention is not intended to be limited to servicing a turbine blade.
  • the damaged portion 12 that is to be replaced according to this embodiment comprises a damaged tip section 12, which is shown in dashed lines in Fig. 1.
  • the damaged tip section 12 of the blade 10 is removed via any appropriate conventional procedure, such as cutting, milling, grinding, etc., or non-conventional procedure, such as electro discharge machining (EDM), laser or water jet cutting, etc.
  • EDM electro discharge machining
  • laser or water jet cutting etc.
  • an outer surface 14 of the blade 10 adjacent to the location of the removed damaged tip section 12 is machined to form an outer mating surface 16. Any conventional procedure can be performed to remove material from the outer surface 14 of the blade 10 so as to form the outer mating surface 16, such as, for example, milling, grinding, electro- discharge machining, water jet machining, etc.
  • the outer mating surface 16 comprises a stepped surface 18 with the adjacent portion of the outer surface 14 of the blade 10, see Figs. 3 and 4.
  • a powder coupon 20 is provided to replace the damaged tip section 12 of the blade 10.
  • the powder coupon 20 comprises powder particles that are at most partially sintered or are bonded together with a binder such as a synthetic wax or a polymeric binder, such as polyetylene.
  • the phase "at most partially sintered” as used herein refers to a state of the power coupon 20 wherein the powder particles that form the powder coupon 20 are either not sintered or are partially sintered such that the coupon 20 is able to be structurally held together, but not fully sintered, wherein the phrase "fully sintered” refers to a state of the powder coupon 20 wherein the powder particles forming the coupon 20 haven been completely or have been almost completely sintered to achieve a density of at least about 98% so as to form a fully consolidated component.
  • the powder particles forming the powder coupon 20 are preferably metallic particles but could also be other types of particles used in powder metallurgy procedures, such as, for example, ceramic particles.
  • the powder coupon 20 comprises a main body 22 and a rim 24 that extends outwardly from a perimeter of the main body 22.
  • An inner surface of the rim 24 defines an inner mating surface 26 of the powder coupon 20, see Fig. 4.
  • a height H R of the rim 24 may be at least about 1/3 of an overall height H P of the powder coupon 20, and is preferably about one half of the overall height H P of the powder coupon 20.
  • a bonding agent 30 preferably including a substance of the type used in transient liquid phase bonding, such as, for example, a nickel (Ni) based alloy such as NiFlex 1 10, 1 15, 120 or 121 bonding alloy agents, which typically contain a balance of Ni with about 9-10% Cr, 5-10% Co, 0-4% Ti, 0-4% Al, 2-5 % W, 0-2% Mo, 0-4% Ta and 0-1 % Hf, is applied to at least one of the outer mating surface 16 of the blade 10 and the inner mating surface 26 of the powder coupon 20.
  • the bonding agent 30 also preferably includes a melting point suppressant substance, e.g., boron, silicon, germanium, etc., which is provided to lower the melting point of the bonding agent 30.
  • the powder coupon 20 is then positioned over the blade 10 such that the inner mating surface 26 of the powder coupon 20 is located adjacent to the outer mating surface 16 of the blade 10 with the bonding agent 30 therebetween.
  • an initial width W P i of the powder coupon 20 is slightly larger than a width WB of the blade 10, thus allowing the powder coupon 20 to be positioned over the blade 10 without the mating surfaces 16, 26 contacting one another.
  • This assemblage of the blade 10, the powder coupon 20, and the bonding agent 30 forms a replacement assembly RA, which is heated using any conventional heating procedure, such as, for example, by placing the replacement assembly R A in a furnace (not shown).
  • the applied heat fully sinters the powder particles of the powder coupon 20 so as to bind the powder particles together.
  • the binding of the powder particles together effects a shrinkage of the powder coupon, thus causing the powder coupon 20 to shrink onto the blade 10 and thus providing a pressure to the outer mating surface 16 of the blade 10 to aid the bonding process, e.g., by eliminating pores/closing gaps between the powder coupon 20 and the blade 10, wherein the applied pressure further eliminates the need for fixturing of the powder coupon 20 to the blade 10, thus simplifying the bonding process.
  • a resulting fully sintered width W P2 of the powder coupon 20, which is now shrunken as a result of the sintering of the powder particles is generally equal to the width W B of the blade 10, see Fig. 5.
  • the applied heat further activates the bonding agent 30 to bond the inner mating surface 26 of the shrunken powder coupon 30 to the outer mating surface 16 of the blade 10, wherein the rim 24 of the powder coupon 20 is received by the stepped surface 18 defined by the outer mating surface 16 and the adjacent portion of the outer surface 14 of the blade 10.
  • the height H R of the rim 24 is preferably about 1/2 of the overall height H P of the powder coupon 20
  • a contact area of the bond between the powder coupon 20 and the blade 10 is large enough to create a secure connection therebetween, which is believed to be able to withstand the forces and temperatures exerted on the replacement assembly RA once installed in a turbine engine.
  • the bonding agent 30 preferably includes a melting point suppressant substance, a lesser amount of heat is required to activate the bonding agent 30 than if the bonding agent 30 did not include a melting point suppressant substance.
  • the applied heat to the replacement assembly RA does not sinter the material forming the blade 10, i.e., since the blade 10 was fully consolidated before the heat was applied to the replacement assembly RA, the applied heat may create a rejuvenation treatment for the blade 10 by restoring the original microstructure of the blade 10.
  • the blade 10 is formed from a nickel based superalloy
  • heating the blade 10 to a temperature near or above the gamma prime solvus temperature associated with the nickel based superalloy forming the blade 10 will cause solutioning of the strengthening gamma prime particles within the superalloy.
  • the gamma prime will then reprecipitate on cooling such that the coarse over aged gamma prime generated during long term and high temperature service exposure can be restored substantially to its original morphology.
  • the bond joint between the blade 10 and the powder coupon 20 is formed between two generally planar surfaces in the embodiment shown, features such as interlocking groves and corresponding ridges maybe present on the surfaces of the blade 10 and the powder coupon 20 to produce a mechanically interlocked joint.
  • a cold working or peening procedure may be performed on the outer and/or inner mating surfaces 16, 26 of the blade 10 and/or the powder coupon 20 so as to create a storage of energy in the respective component.
  • the storage of energy is believed to aid in recrystallization and grain growth of the crystals of the respective component so as to effect a strengthening of the bond between the powder coupon 20 and the blade 10.
  • cooling features such as, for example, cooling holes, turbulating features, etc.
  • cooling features could be formed in the blade 10 and/or the powder coupon 20 before they are bonded together. If formed in the powder coupon 20, such cooling features could be formed in the powder coupon 20 either during molding, in the green state, or after partial sintering.
  • inventive aspects described herein enable the replacement of a damaged portion of a turbine engine component using a unique combination of powder metallurgy and transient liquid phase bonding as an alternative approach to replacing the entire component
  • inventive aspects described herein could also apply to the formation of new components.
  • a new component portion such as a blade tip
  • a remaining portion of the component such as a remaining portion of a blade, using the methods described herein.
  • inventive aspects described herein could be used to repair or form other components for use in turbine engines, such as, for example, stationary vanes, ring segments, seals, transition panels, etc.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Materials Engineering (AREA)
  • Powder Metallurgy (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Adhesives Or Adhesive Processes (AREA)

Abstract

A removed damaged portion of a fully consolidated turbine engine component is replaced with a powder coupon that includes powder particles that are at most partially sintered or are bonded together with a binder. A bonding agent is applied to the component and/or the powder coupon. The powder coupon is then positioned over the component and heat is applied to fully sinter the powder particles, thus causing the powder coupon to shrink onto the component. The heat also activates the bonding agent to bond the shrunken powder coupon to the component, but the heat does not sinter the material forming the fully consolidated component.

Description

METHOD FOR REPAIRING A COMPONENT FOR USE IN A TURBINE ENGINE
FIELD OF THE INVENTION
The present invention relates to repairing fully consolidated components for use in turbine engines using partially sintered or bonded powder coupons that are shrunken onto and bonded to the fully consolidated component with a bonding agent.
BACKGROUND OF THE INVENTION
In a turbomachine, such as a gas turbine engine, air is pressurized in a compressor section then mixed with fuel and burned in a combustion section to generate hot combustion gases. The hot combustion gases are expanded within a turbine section of the engine where energy is extracted to provide output power used to produce electricity. The hot combustion gases travel through a series of stages when passing through the turbine section. A stage may include a row of stationary airfoils, i.e., vanes, followed by a row of rotating airfoils, i.e., blades, where the blades extract energy from the hot combustion gases for providing output power.
Since the components within the combustion section and the turbine section are directly exposed to the hot combustion gases, these components may become damaged and in need of repair.
SUMMARY OF THE INVENTION
In accordance with a first aspect of the present invention, a method is provided for replacing a removed damaged portion of a fully consolidated component for use in a turbine engine. A powder coupon is provided comprising powder particles that are at most partially sintered or are bonded together with a binder. A bonding agent is applied to at least one of an outer mating surface of the component and an inner mating surface of the powder coupon. The powder coupon is positioned over the component such that the inner mating surface of the powder coupon is located adjacent to the outer mating surface of the component with the bonding agent therebetween so as to form a replacement assembly comprising the component, the powder coupon, and the bonding agent. Heat is applied to the replacement assembly, wherein the applied heat fully sinters the powder particles of the powder coupon so as to bind the powder particles together, thus causing the powder coupon to shrink onto the component. The applied heat also activates the bonding agent to bond the inner mating surface of the shrunken powder coupon to the outer mating surface of the component. However, the applied heat to the replacement assembly does not sinter the material forming the fully consolidated component.
In accordance with a second aspect of the present invention, a method is provided for repairing a fully consolidated component for use in a turbine engine. A damaged portion of the component is removed, and an outer surface of the component adjacent to the location of the removed damaged portion is machined using a material removal procedure to form an outer mating surface comprising a stepped surface with an adjacent portion of the outer surface of the component. A powder coupon is provided comprising powder particles that are at most partially sintered or are bonded together with a binder. A bonding agent is applied to at least one of the outer mating surface of the component and an inner mating surface of the powder coupon. The powder coupon is positioned over the component such that the inner mating surface of the powder coupon is located adjacent to the outer mating surface of the component with the bonding agent therebetween so as to form a replacement assembly comprising the component, the powder coupon, and the bonding agent. Heat is applied to the replacement assembly, wherein the applied heat fully sinters the powder particles of the powder coupon so as to bind the powder particles together, thus causing the powder coupon to shrink such that the inner mating surface of the powder coupon is shrunken onto the outer mating surface of the component with the bonding agent therebetween. The applied heat also activates the bonding agent to bond the inner mating surface of the shrunken powder coupon to the outer mating surface of the component. The shrinking of the powder coupon onto the component exerts a pressure on the outer mating surface of the component so as to aid in the bonding process between the inner mating surface of the shrunken powder coupon and the outer mating surface of the component. The applied heat to the replacement assembly does not sinter the material forming the fully consolidated component. BRIEF DESCRIPTION OF THE DRAWINGS
While the specification concludes with claims particularly pointing out and distinctly claiming the present invention, it is believed that the present invention will be better understood from the following description in conjunction with the accompanying Drawing Figures, in which like reference numerals identify like elements, and wherein:
Fig. 1 is a schematic illustration of a component for use in a turbine engine of the type to be serviced in accordance with the present invention, wherein the component includes a damaged portion;
Fig. 2 is a schematic illustration of the component illustrated in Fig. 1 after a step of a servicing operation has been implemented to remove the damaged portion from the component;
Figs. 3 and 4 are perspective (Fig. 3) and schematic (Fig. 4) illustrations of the component of Fig. 1 undergoing another step in the servicing operation; and
Fig. 5 is a schematic illustration of the component of Fig. 1 after it has undergone the servicing operation according to the present invention.
DETAILED DESCRIPTION OF THE INVENTION
In the following detailed description of the preferred embodiment, reference is made to the accompanying drawings that form a part hereof, and in which is shown by way of illustration, and not by way of limitation, a specific preferred embodiment in which the invention may be practiced. It is to be understood that other embodiments may be utilized and that changes may be made without departing from the spirit and scope of the present invention.
After periods of use, it may become necessary to replace portions of turbine engine components, such as, for example, turbine airfoils, i.e., rotating blades and stationary vanes. In accordance with the present invention, a method for servicing a turbine engine component has been developed.
Referring to Fig. 1 , a turbine engine component 10 of the type to be serviced according to an aspect of the present invention is illustrated. In the exemplary embodiment illustrated, the component 10 is a turbine blade 10 having a damaged portion 12 to be replaced, although it is noted that the invention is not intended to be limited to servicing a turbine blade. The damaged portion 12 that is to be replaced according to this embodiment comprises a damaged tip section 12, which is shown in dashed lines in Fig. 1.
The damaged tip section 12 of the blade 10 is removed via any appropriate conventional procedure, such as cutting, milling, grinding, etc., or non-conventional procedure, such as electro discharge machining (EDM), laser or water jet cutting, etc.
Referring to Fig. 2, once the damaged tip section 12 of the blade 10 is removed, an outer surface 14 of the blade 10 adjacent to the location of the removed damaged tip section 12 is machined to form an outer mating surface 16. Any conventional procedure can be performed to remove material from the outer surface 14 of the blade 10 so as to form the outer mating surface 16, such as, for example, milling, grinding, electro- discharge machining, water jet machining, etc. The outer mating surface 16 comprises a stepped surface 18 with the adjacent portion of the outer surface 14 of the blade 10, see Figs. 3 and 4.
Referring now to Figs. 3 and 4, a powder coupon 20 is provided to replace the damaged tip section 12 of the blade 10. The powder coupon 20 comprises powder particles that are at most partially sintered or are bonded together with a binder such as a synthetic wax or a polymeric binder, such as polyetylene. The phase "at most partially sintered" as used herein refers to a state of the power coupon 20 wherein the powder particles that form the powder coupon 20 are either not sintered or are partially sintered such that the coupon 20 is able to be structurally held together, but not fully sintered, wherein the phrase "fully sintered" refers to a state of the powder coupon 20 wherein the powder particles forming the coupon 20 haven been completely or have been almost completely sintered to achieve a density of at least about 98% so as to form a fully consolidated component.
The powder particles forming the powder coupon 20 are preferably metallic particles but could also be other types of particles used in powder metallurgy procedures, such as, for example, ceramic particles.
The powder coupon 20 comprises a main body 22 and a rim 24 that extends outwardly from a perimeter of the main body 22. An inner surface of the rim 24 defines an inner mating surface 26 of the powder coupon 20, see Fig. 4. As shown in Fig. 4, a height HR of the rim 24 may be at least about 1/3 of an overall height HP of the powder coupon 20, and is preferably about one half of the overall height HP of the powder coupon 20.
According to an aspect of the present invention, a bonding agent 30, preferably including a substance of the type used in transient liquid phase bonding, such as, for example, a nickel (Ni) based alloy such as NiFlex 1 10, 1 15, 120 or 121 bonding alloy agents, which typically contain a balance of Ni with about 9-10% Cr, 5-10% Co, 0-4% Ti, 0-4% Al, 2-5 % W, 0-2% Mo, 0-4% Ta and 0-1 % Hf, is applied to at least one of the outer mating surface 16 of the blade 10 and the inner mating surface 26 of the powder coupon 20. The bonding agent 30 also preferably includes a melting point suppressant substance, e.g., boron, silicon, germanium, etc., which is provided to lower the melting point of the bonding agent 30.
The powder coupon 20 is then positioned over the blade 10 such that the inner mating surface 26 of the powder coupon 20 is located adjacent to the outer mating surface 16 of the blade 10 with the bonding agent 30 therebetween. As shown most clearly in Fig. 4, an initial width WPi of the powder coupon 20 is slightly larger than a width WB of the blade 10, thus allowing the powder coupon 20 to be positioned over the blade 10 without the mating surfaces 16, 26 contacting one another.
This assemblage of the blade 10, the powder coupon 20, and the bonding agent 30 forms a replacement assembly RA, which is heated using any conventional heating procedure, such as, for example, by placing the replacement assembly RA in a furnace (not shown). The applied heat fully sinters the powder particles of the powder coupon 20 so as to bind the powder particles together. The binding of the powder particles together effects a shrinkage of the powder coupon, thus causing the powder coupon 20 to shrink onto the blade 10 and thus providing a pressure to the outer mating surface 16 of the blade 10 to aid the bonding process, e.g., by eliminating pores/closing gaps between the powder coupon 20 and the blade 10, wherein the applied pressure further eliminates the need for fixturing of the powder coupon 20 to the blade 10, thus simplifying the bonding process. A resulting fully sintered width WP2 of the powder coupon 20, which is now shrunken as a result of the sintering of the powder particles, is generally equal to the width WB of the blade 10, see Fig. 5.
The applied heat further activates the bonding agent 30 to bond the inner mating surface 26 of the shrunken powder coupon 30 to the outer mating surface 16 of the blade 10, wherein the rim 24 of the powder coupon 20 is received by the stepped surface 18 defined by the outer mating surface 16 and the adjacent portion of the outer surface 14 of the blade 10. Since the height HR of the rim 24 is preferably about 1/2 of the overall height HP of the powder coupon 20, a contact area of the bond between the powder coupon 20 and the blade 10 is large enough to create a secure connection therebetween, which is believed to be able to withstand the forces and temperatures exerted on the replacement assembly RA once installed in a turbine engine. Further, since the bonding agent 30 preferably includes a melting point suppressant substance, a lesser amount of heat is required to activate the bonding agent 30 than if the bonding agent 30 did not include a melting point suppressant substance.
It is noted that while the applied heat to the replacement assembly RA does not sinter the material forming the blade 10, i.e., since the blade 10 was fully consolidated before the heat was applied to the replacement assembly RA, the applied heat may create a rejuvenation treatment for the blade 10 by restoring the original microstructure of the blade 10. For example, if the blade 10 is formed from a nickel based superalloy, heating the blade 10 to a temperature near or above the gamma prime solvus temperature associated with the nickel based superalloy forming the blade 10 will cause solutioning of the strengthening gamma prime particles within the superalloy. The gamma prime will then reprecipitate on cooling such that the coarse over aged gamma prime generated during long term and high temperature service exposure can be restored substantially to its original morphology.
Moreover, while the bond joint between the blade 10 and the powder coupon 20 is formed between two generally planar surfaces in the embodiment shown, features such as interlocking groves and corresponding ridges maybe present on the surfaces of the blade 10 and the powder coupon 20 to produce a mechanically interlocked joint.
According to an aspect of the present invention, before heat is applied to the replacement assembly RA, a cold working or peening procedure may be performed on the outer and/or inner mating surfaces 16, 26 of the blade 10 and/or the powder coupon 20 so as to create a storage of energy in the respective component. The storage of energy is believed to aid in recrystallization and grain growth of the crystals of the respective component so as to effect a strengthening of the bond between the powder coupon 20 and the blade 10.
Additionally, one or more types of cooling features, such as, for example, cooling holes, turbulating features, etc., could be formed in the blade 10 and/or the powder coupon 20 before they are bonded together. If formed in the powder coupon 20, such cooling features could be formed in the powder coupon 20 either during molding, in the green state, or after partial sintering.
While the inventive aspects described herein enable the replacement of a damaged portion of a turbine engine component using a unique combination of powder metallurgy and transient liquid phase bonding as an alternative approach to replacing the entire component, the inventive aspects described herein could also apply to the formation of new components. For example, a new component portion, such as a blade tip, may be formed by a powder coupon and bonded to a remaining portion of the component, such as a remaining portion of a blade, using the methods described herein. Further, as noted above, the inventive aspects described herein could be used to repair or form other components for use in turbine engines, such as, for example, stationary vanes, ring segments, seals, transition panels, etc.
While particular embodiments of the present invention have been illustrated and described, it would be obvious to those skilled in the art that various other changes and modifications can be made without departing from the spirit and scope of the invention. It is therefore intended to cover in the appended claims all such changes and modifications that are within the scope of this invention.

Claims

CLAIMS What is claimed is:
1. A method for replacing a removed damaged portion of a fully consolidated component for use in a turbine engine comprising:
providing a powder coupon comprising powder particles that are at most partially sintered or are bonded together with a binder;
applying a bonding agent to at least one of an outer mating surface of the component and an inner mating surface of the powder coupon;
positioning the powder coupon over the component such that the inner mating surface of the powder coupon is located adjacent to the outer mating surface of the component with the bonding agent therebetween so as to form a replacement assembly comprising the component, the powder coupon, and the bonding agent; and
applying heat to the replacement assembly, wherein the applied heat:
fully sinters the powder particles of the powder coupon so as to bind the powder particles together, thus causing the powder coupon to shrink onto the component; and
activates the bonding agent to bond the inner mating surface of the shrunken powder coupon to the outer mating surface of the component;
wherein applying heat to the replacement assembly does not sinter the material forming the fully consolidated component.
2. The method according to claim 1 , further comprising machining an outer surface of the component adjacent to the location of the removed damaged portion using a material removal procedure to form the outer mating surface.
3. The method according to claim 2, wherein the outer mating surface of the component comprises a stepped surface with an adjacent portion of the outer surface of the component.
4. The method according to claim 3, wherein the powder coupon comprises a rim that defines the inner mating surface and that is received by the stepped surface of the component when the shrunken powder coupon is bonded to the component.
5. The method according to claim 1 , wherein the inner and outer mating surfaces include features that effect a mechanical interlocking between the shrunken powder coupon and the component
6. The method according to claim 1 , wherein the bonding agent comprises a melting point suppressant substance that lowers the melting point of the bonding agent.
7. The method according to claim 6, wherein the melting point suppressant substance comprises at least one of boron, silicon, and germanium.
8. The method according to claim 1 , further comprising, before applying heat to the replacement assembly, cold working or peening at least one of the outer mating surface of the component and the inner mating surface of the powder coupon to create a storage of energy in the at least one of the component and the powder coupon, wherein the storage of energy effects a strengthening of the bond between the powder coupon and the component.
9. The method according to claim 1 , wherein the component comprises a turbine blade and the removed damaged portion of the component comprises a damaged blade tip.
10. The method according to claim 1 , wherein the applied heat also creates a rejuvenation treatment for the fully consolidated component by substantially restoring the original microstructure of the component.
1 1. A method for repairing a fully consolidated component for use in a turbine engine comprising:
removing a damaged portion of the component;
machining an outer surface of the component adjacent to the location of the removed damaged portion using a material removal procedure to form an outer mating surface comprising a stepped surface with an adjacent portion of the outer surface of the component;
providing a powder coupon comprising powder particles that are at most partially sintered or are bonded together with a binder;
applying a bonding agent to at least one of the outer mating surface of the component and an inner mating surface of the powder coupon;
positioning the powder coupon over the component such that the inner mating surface of the powder coupon is located adjacent to the outer mating surface of the component with the bonding agent therebetween so as to form a replacement assembly comprising the component, the powder coupon, and the bonding agent; and
applying heat to the replacement assembly, wherein the applied heat:
fully sinters the powder particles of the powder coupon so as to bind the powder particles together, thus causing the powder coupon to shrink such that the inner mating surface of the powder coupon is shrunken onto the outer mating surface of the component with the bonding agent therebetween; and
activates the bonding agent to bond the inner mating surface of the shrunken powder coupon to the outer mating surface of the component;
wherein the shrinking of the powder coupon onto the component exerts a pressure on the outer mating surface of the component so as to aid in the bonding process between the inner mating surface of the shrunken powder coupon and the outer mating surface of the component;
wherein applying heat to the replacement assembly does not sinter the material forming the fully consolidated component.
12. The method according to claim 1 1 , wherein the bonding agent comprises a melting point suppressant substance that lowers the melting point of the bonding agent.
13. The method according to claim 12, wherein the melting point suppressant substance comprises at least one of boron, silicon, and germanium.
14. The method according to claim 1 1 , further comprising, before applying heat to the replacement assembly, cold working or peening at least one of the outer mating surface of the component and the inner mating surface of the powder coupon to create a storage of energy in the at least one of the component and the powder coupon, wherein the storage of energy effects a strengthening of the bond between the powder coupon and the component.
15. The method according to claim 1 1 , wherein the powder coupon comprises a rim that defines the inner mating surface and that is received by the stepped surface of the component when the shrunken powder coupon is bonded to the component.
16. The method according to claim 15, wherein a height of the rim is at least about 1/3 of an overall height of the powder coupon.
17. The method according to claim 1 1 , wherein the component comprises a turbine blade and the damaged portion of the component comprises a damaged blade tip.
18. The method according to claim 1 1 , further comprising forming at least one cooling feature in the powder coupon prior to applying heat to the replacement assembly.
19. The method according to claim 18, wherein the at least one cooling feature comprises at least one of a cooling hole and a turbulating feature.
20. The method according to claim 1 1 , wherein the applied heat also creates a rejuvenation treatment for the fully consolidated component by substantially restoring the original microstructure of the component.
EP13779463.2A 2012-10-03 2013-10-02 Method for repairing a component for use in a turbine engine Withdrawn EP2903764A1 (en)

Applications Claiming Priority (2)

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US13/633,999 US9700941B2 (en) 2012-10-03 2012-10-03 Method for repairing a component for use in a turbine engine
PCT/US2013/063066 WO2014055646A1 (en) 2012-10-03 2013-10-02 Method for repairing a component for use in a turbine engine

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EP (1) EP2903764A1 (en)
JP (1) JP2015533987A (en)
KR (1) KR20150063548A (en)
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WO (1) WO2014055646A1 (en)

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JP2015533987A (en) 2015-11-26
US9700941B2 (en) 2017-07-11
CN104703733A (en) 2015-06-10
WO2014055646A1 (en) 2014-04-10
KR20150063548A (en) 2015-06-09

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